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CFR Citation: 14 CFR Part 39

Docket ID: [Docket No. FAA-2007-27012; Directorate Identifier 2006-NM-188-AD; Amendment 39-15017; AD 2007-07-15]

RIN ID: RIN 2120-AA64

NOTICE: RULES

ACTION: Airworthiness directives:

DOCUMENT ACTION: Final rule.

SUBJECT CATEGORY: Airworthiness Directives; Airbus Model A300 B4-601, A300 B4-603, A300 B4-605R, A300 C4-605R Variant F, A310-204, and A310-304 Airplanes Equipped With General Electric CF6-80C2 Engines

DATES: This AD becomes effective May 14, 2007.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of May 14, 2007.

On May 13, 2004 (69 FR 23090, April 28, 2004), the Director of the Federal Register approved the incorporation by reference of Airbus All Operators Telex A31054A2038, dated February 19, 2004; and Airbus All Operators Telex A30054A6037, dated February 19, 2004.
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DOCUMENT SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A300 B4600, B4600R, C4 605R Variant F, and F4600R (collectively called A300600) series airplanes; and Model A310 series airplanes. That AD currently requires a onetime inspection for damage of the integrated drive generator (IDG) electrical harness and pyramid arm, and repair if necessary. This new AD adds new repetitive inspections, which, when initiated, terminate the inspection required by the existing AD. This new AD also requires repairing damage and protecting the harness. This new AD also provides for optional terminating action for the repetitive inspections. This new AD also removes certain airplanes from the applicability of the existing AD. This AD results from a report of structural damage on the forward pyramid arm of an engine pylon due to chafing of the IDG electrical harness against the structure of the pyramid arm. We are issuing this AD to prevent electrical arcing in the engine pylon, which could result in loss of the relevant alternating current (AC) bus bar, reduced structural integrity of the engine pylon, and possible loss of control of the airplane.

SUMMARY: Airbus,

SUPPLEMENTAL INFORMATION

You may examine the airworthiness directive (AD) docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 6475227) is located on the plaza level of the Nassif Building at the street address stated in the ADDRESSES section. Discussion

The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 20040901, amendment 3913590 (69 FR 23090, April 28, 2004). The existing AD applies to certain Airbus Model A300 B4600, B4600R, C4605R Variant F, and F4 600R (collectively called A300600) series airplanes; and Model A310 series airplanes. That NPRM was published in the Federal Register on January 26, 2007 (72 FR 3764). That NPRM proposed to require a onetime inspection for damage of the integrated drive generator (IDG) electrical harness and pyramid arm, and repair if necessary. That NPRM proposed to add new repetitive inspections, which, when initiated, would terminate the inspection required by the existing AD. That NPRM also proposed to require repairing damage and protecting the harness. That NPRM also proposed to provide for optional terminating action for the repetitive inspections. That NPRM also proposed to remove certain airplanes from the applicability of the existing AD.

Comments

We provided the public the opportunity to participate in the development of this AD. No comments have been received on the NPRM or on the determination of the cost to the public.

Change to Applicability

We have removed Airbus Model A310308 airplanes from the applicability of this AD. That model is not listed as an FAAcertified model in our type certificate data sheets.

Conclusion

We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD with the change described previously. We have determined that this change will neither increase the economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

The following table provides the estimated costs for U.S. operators to comply with this AD.
Estimated Costs Average
Work labor Cost of Cost per Number of U.S. Action hours rate per parts airplane registered Fleet cost hour airplanes Onetime inspection (from AD 2 $80 $0 $160........... 100............ $16,000. 20040901).
Repetitive inspections and 4 80 0 $320, per 100............ $32,000, per harness protection (new inspection inspection requirement). cycle. cycle. New optional modification... 8 80 2,460 $3,100......... Up to 100...... Up to $310,000. Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority.

We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.

Regulatory Findings

We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government.

For the reasons discussed above, I certify that this AD: (1) Is not a ``significant regulatory action'' under Executive Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.

We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows:
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PART 39AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by removing amendment 3913590 (69 FR 23090, April 28, 2004) and by adding the following new airworthiness directive (AD):
20070715 Airbus: Amendment 3915017. Docket No. FAA200727012; Directorate Identifier 2006NM188AD.
Effective Date
(a) This AD becomes effective May 14, 2007.
Affected ADs
(b) This AD supersedes AD 20040901.
Applicability
(c) This AD applies to Airbus Model A300 B4601, A300 B4603, A300 B4605R, A300 C4605R Variant F, A310204, and A310304
airplanes; certificated in any category; equipped with General Electric CF680C2 engines without fullauthority digital electronic control (FADEC); excluding airplanes on which Airbus Modification 13184 was done in production.
Unsafe Condition
(d) This AD results from a report of structural damage on the forward pyramid arm of an engine pylon due to chafing of the integrated drive generator (IDG) electrical harness against the structure of the pyramid arm. We are issuing this AD to prevent electrical arcing in the engine pylon, which could result in loss of the relevant alternating current (AC) bus bar, reduced structural integrity of the engine pylon, and possible loss of control of the airplane.
Compliance
(e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Restatement of Certain Requirements of AD 20040901
All Operators Telex Reference
(f) The term ``All Operators Telex,'' or ``AOT,'' as used in paragraphs (g), (h), and (j) of this AD, means the following AOTs, as applicable:
(1) For Model A300 B4601, A300 B4603, A300 B4605R, and A300 C4605R Variant F airplanes: Airbus AOT A30054A6037, dated February 19, 2004; and
(2) For Model A310204, and A310304 airplanes: Airbus AOT A310 54A2038, dated February 19, 2004.
Inspection
(g) At the applicable time in paragraph (g)(1) or (g)(2) of this AD, do a onetime detailed inspection for discrepancies of the IDG harness, harness bracket, retaining fasteners, and pyramid arm, in accordance with the applicable AOT.
(1) For airplanes on which Airbus Modification 07591 has not been incorporated as of May 13, 2004 (the effective date of AD 2004 0901): Within 10 days after May 13, 2004.
(2) For airplanes on which Airbus Modification 07591 has been incorporated as of May 13, 2004: Within 600 flight hours after May 13, 2004.

Note 1: For the purposes of this AD, a detailed inspection is defined as: ``An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally
supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.''
Related Investigative and Corrective Actions for Damaged Electrical Harness
(h) If any discrepancy in the IDG electrical harness, fretting at the convoluted conduits, or contact between the IDG electrical harness and the pyramid arms is found during the inspection required by paragraph (g) of this AD: Before further flight, do the applicable related investigative actions and corrective actions in accordance with the applicable AOT.
Corrective Action for Damaged Electrical Harness Bracket, Retaining Fasteners, or Pyramid Arm
(i) If any discrepancy in the electrical harness bracket, retaining fasteners, or pyramid arm is found during the inspection required by paragraph (g) of this AD: Before further flight, repair in accordance with a method approved by the Manager, International Branch, ANM116, Transport Airplane Directorate, FAA; the Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated agent); or the European Aviation Safety Agency (EASA) (or its delegated agent). After the effective date of this AD, repair in accordance with a method approved by the FAA or the EASA.
No Reporting Requirement for Paragraph (g) of this AD
(j) Although the referenced AOTs describe procedures for submitting certain information to the manufacturer, no report is required for the inspection required by paragraph (g) of this AD. New Requirements of this AD
Repetitive Inspections
(k) Within 6 months after the effective date of this AD, and thereafter at intervals not to exceed 12 months: Do a detailed inspection for damage of the IDG harness and the pylon pyramid arms, and protect the harness. Do the actions in accordance with Airbus Service Bulletin A300246097, dated March 3, 2006 (for Model A300 B4601, A300 B4603, A300 B4605R, and A300 C4605R Variant F
airplanes); or A310242100, dated March 3, 2006 (for Model A310 204, and A310304 airplanes). The initial inspection terminates the requirements of paragraph (g) of this AD. If any discrepancy is found: Before further flight, repair in accordance with the applicable service bulletin; except, where the service bulletin specifies to contact the manufacturer for repair instructions, this AD requires repair using a method approved by either the Manager, International Branch, ANM116; or the EASA (or its delegated agent). Report
(l) At the applicable times specified in paragraphs (l)(1) and (l)(2) of this AD, submit a report of the findings (both positive and negative) of each inspection required by paragraph (k) of this AD. Send the report to Airbus Customer Services Directorate, Department AI/SEE43, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. The report must include the information specified in Appendix 01 of Airbus Service Bulletin A300246097 or A310242100, both dated March 3, 2006, as applicable. Under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 21200056.
(1) For each inspection done after the effective date of this

FOR FURTHER INFORMATION CONTACT Tom Stafford, Aerospace Engineer, International Branch, ANM116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 980573356; telephone (425) 2271622; fax (425) 2271149.